Browse Topic: Aircraft propulsion systems

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Aircraft and Aircraft Engine Fuel Pump Low Lubricity Fluid Endurance TestARP1797B (Current)11/26/2025
This procedure is intended to apply to fuel pumps. This procedure will be defined in terms of recommended test fluid, test setup, test conditions, and test method. This procedure may be used for other fuel system components, by testing in conjunction with the pump, which normally supplies the component inlet flow, or a substitute test pump of similar capacity. This procedure may be used, with variations in test conditions and test fluid for performing pump evaluation tests. Tests at progressively increasing pump speeds and pressures will provide design limitation data. Alternate test periods on a test pump and another pump, of a design for which actual service durability is known, will provide useful comparison data.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
On-Board Fuel Sensing for UAS and Ground Vehicle Applications2024-01-412809/16/2024
Abstract The variability in fuel, particularly for fuel blends containing sustainable aviation fuels (SAFs), emphasizes the importance of understanding fuel properties for optimizing engine performance. This paper introduces spectroscopic fuel sensors capable of real-time estimation of jet fuel properties, mainly derived cetane number (DCN). While initially developed for unmanned aircraft systems (UAS), the paper explores their potential in ground vehicle applications: enhancing engine performance through sensing for feed-forward control and fuel property monitoring at fuel depots. The fuel sensing technologies are based on spectroscopic techniques coupled with machine learning (ML) approaches. The combination of these techniques demonstrates a promising solution for a wide spectrum of fuel applications.
Patel, Dev B., Sutar, Ashish, Abraham, Abhinav, Ambre, Dhananjay, Brezinsky, Kenneth, Lynch, Patrick T., Okada, Haruna, Stafford, Jacob M., Miganakallu, Niranjan, Sanders, Scott, Rothamer, David, Mayhew, Eric, Kim, Kenneth S.
Infrared Signature of Fixed and Variable Area C-D Nozzle of Aircraft Engine88-16-02-001101/02/2023
The use of converging-diverging (C-D) variable area nozzle (VAN) in military aeroengines is now common, as it can give optimal expansion and control over engine back pressure, for a wide range of engine operations. At higher main combustion temperatures (desired for supercruise), an increase in the nozzle expansion ratio is needed for optimum performance. But changes in the nozzle throat and exit areas affect the visibility of engine hot parts as the diverging section of the nozzle is visible for a full range of view angle from the rear aspect. The solid angle subtended by engine hot parts varies with change in visibility, which affects the aircraft infrared (IR) signature from the rear aspect. This study compares the performances of fixed and variable area nozzles (FAN and VAN) in terms of engine thrust and IR signature of the engine exhaust system in the boresight for the same increase in combustion temperature. This study is performed for two cases: (i) variable throat area and
Baranwal, Nidhi, Mahulikar, Shripad P.
Infrared Signature of Fixed and Variable Area C-D Nozzle of Aircraft Engine01-16-02-001101/02/2023
The use of converging-diverging (C-D) variable area nozzle (VAN) in military aeroengines is now common, as it can give optimal expansion and control over engine back pressure, for a wide range of engine operations. At higher main combustion temperatures (desired for supercruise), an increase in the nozzle expansion ratio is needed for optimum performance. But changes in the nozzle throat and exit areas affect the visibility of engine hot parts as the diverging section of the nozzle is visible for a full range of view angle from the rear aspect. The solid angle subtended by engine hot parts varies with change in visibility, which affects the aircraft infrared (IR) signature from the rear aspect. This study compares the performances of fixed and variable area nozzles (FAN and VAN) in terms of engine thrust and IR signature of the engine exhaust system in the boresight for the same increase in combustion temperature. This study is performed for two cases: (i) variable throat area and
Baranwal, Nidhi, Mahulikar, Shripad P.
Blockchain based Aircraft Maintenance Records2022-26-114005/26/2022
Currently, Aircraft records and many other archives are in paper format. Paper records like maintenance records included in logbook are cumbersome, inefficient, and insecure compared to the capabilities of modern technology. Blockchain technology is the next step in creating process efficiencies, security, and integrity of maintenance data over the lifetime of an aircraft/engine. Changing paper records to digital records using blockchain is the foundation for a better future towards digital twin and analytics. Blockchain based maintenance can connect a world of data between various groups for extended periods of time by creating a secure digital thread. As regulatory requirements grow and cyber threats loom, blockchain technology can assist in the integrity and security of the captured data. The objective of this paper is to describe the advantages of migrating to digital applications using blockchain and how it can secure the future of the industry.
Jayarajan, Keerthi
Hydrogen Fueled Aircraft Engines2022-26-115605/26/2022
In the recent years, the climate change has become more devastating, and its continuing use of fossil fuels seems unreasonable as humankind is being pushed into a corner where the need to choose an alternative fuel has become necessary. The two main alternatives currently available are: Electrical propulsion and Hydrogen injected air breathing engines. Electrical propulsion had come far since last 10 years with Li+ ion technology, but the problem with them persists. They provide a low power to weight ratio which reduces the range as well as the load while operating the aircraft. On the other hand, Hydrogen with fuel cells or H2-O2 combustion has a high power to weight ratio but very difficult to handle. So, using hydrogen comes with a lot of difficulties in the present scenario. However. the concept of hydrogen has come a long way since its first use as a Rocket fuel. But this alternate fuel provides many advantages as well as challenges which needs to be overcome to move on its use in
Sri, Ratan, Sivamani, Seralathan
Energy Scavenging from Passengers for Powering Low-energy Electronics in Aircrafts2022-26-125505/26/2022
With the ever increasing demand for aerial modes of transportation and reduction of different harmful emissions from these modes of transportation has led to demand for more electric modes of powering these aerial vehicles. In addition to that, the aerospace industry is also looking to make the aircrafts more smart and more connected. This involves increased use of more sensors, ICs and many more micro-electronic components. Even though they look small and consume less electricity, the electric battery which is supposed to be used for aircraft propulsion will require to power up these smaller components as well, which will continue to be a concern as the aircrafts begin using more and more of these components. Hence, a solution is needed to reduce the dependency of micro-electronic components or any other aircraft components used within the aircraft on the electric battery to be used for aircraft propulsion. The concept of Energy Harvesting or Energy Scavenging refers to the capturing
Bajpai, Apoorva
RM13006 - Process Control MethodsAESQRM00620210909/07/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
SAE TOMORROW TODAY: Cleaner, Greener & Quieter: Transforming the Future of Flying1316109/03/2021
The best airplane can only be designed around the best engine - so says Pratt & Whitney, a Raytheon Technologies Company, where they've been transforming powered flight with an explorer's heart and a perfectionist's grit. Lisa Claveloux, Pratt & Whitney's Senior Director, Group Quality, tells the iconic brand's history, what impacts the pandemic has had on the aerospace industry, and the more sustainable footprint that their GTF engines bring to the skies. These revolutionary geared turbofan engines have already saved more than half a billion gallons of fuel and about five million metric tonnes of CO2, while also slashing aircraft noise footprint by 75%. Claveloux's passion for safety drew her to the work of the SAE ITC Aerospace Engine Supplier Quality (AESQ) strategy group. She discusses the challenges in the market, the gap the SAE AS13100 Standard fills, and why compliance is critical for enabling quality and making our skies safe for everyone.
Hineman, Marcie
RM13003 - Measurement Systems AnalysisAESQRM00320210505/17/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
Gas Turbine Engine Performance Presentation for Computer Programs Using FortranAS4191A (Current)05/13/2021
This SAE Aerospace Standard (AS) provides a method for gas turbine engine performance computer programs to be written using Fortran COMMON blocks. If a “function-call application program interface” (API) is to be used, then ARP4868 and ARP5571 are recommended as alternatives to that described in this document. When it is agreed between the program user and supplier that a particular program shall be supplied in Fortran, this document shall be used in conjunction with AS681 for steady-state and transient programs. This document also describes how to take advantage of the Fortran CHARACTER storage to extend the information interface between the calling program and the engine subroutine.
S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces
RM13004 - Defect Prevention Quality Tools to Support APQP & PPAPAESQRM00420210303/25/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
RM13102 - First Article InspectionAESQRM10220210303/15/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
RM13145 - Advanced Product Quality Planning (APQP) and Production Part Approval Process (PPAP) within AerospaceAESQRM14520210303/15/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
RM13011 - Rework and Production Repair of Non-Conforming ProductsAESQRM01120210303/15/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
RM13002 - Alternate Inspection Frequency PlansAESQRM00220210303/08/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
RM13006 - Process Control MethodsAESQRM00620210303/08/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
RM13000 - 8D Problem Solving MethodAESQRM00020210303/08/2021
AS13100 AESQ Quality Management System Requirements for Aero Engine Design and Production Organizations Standard was created to replace customer specific quality requirements – leading to simplification and harmonization between engine manufacturer supply chains. AS13100 is supported by a series of 13 AESQ Reference Manuals (RM) that provide additional detail on certain subjects to describe the intent of the standard and to provide guidance on deployment. The Reference Manuals are designed to enable the supply chain to deploy the AS13100 requirements efficiently and effectively. The AESQ RMs provide case studies, guidance material, forms and checklists specific to each section of the standard to aid the user with implementation.
Aerospace Engine Supplier Quality Strategy Group
Lubricating Oils, Aircraft Piston Engine (Non-Dispersant Mineral Oil)J1966_202010 (Current)10/28/2020
This SAE Standard establishes the requirements for nondispersant, mineral lubricating oils to be used in four-stroke cycle piston aircraft engines. This document covers the same lubricating oil requirements as the former military specification MIL-L-6082. Users should consult their airframe or engine manufacturers manuals for the latest listing of acceptable lubricants.
E-38 Aviation Piston Engine Fuels and Lubricants
Lubricating Oil, Aircraft Piston Engine (Ashless Dispersant)J1899_202010 (Current)10/28/2020
This SAE Standard establishes the requirements for lubricating oils containing ashless dispersant additives to be used in four-stroke cycle, reciprocating piston aircraft engines. This document covers the same lubricating oil requirements as the former military specification MIL-L-22851. Users should consult their airframe or engine manufacturers manuals for the latest listing of acceptable lubricants.
E-38 Aviation Piston Engine Fuels and Lubricants
Lubricating Oils, Aircraft Piston Engine (Non-Dispersant Mineral Oil)J1966_202010-TEST-REC (Historical)10/28/2020
This SAE Standard establishes the requirements for nondispersant, mineral lubricating oils to be used in four-stroke cycle piston aircraft engines. This document covers the same lubricating oil requirements as the former military specification MIL-L-6082. Users should consult their airframe or engine manufacturers manuals for the latest listing of acceptable lubricants.
E-38 Aviation Piston Engine Fuels and Lubricants
Lubricating Oil, Aircraft Piston Engine (Ashless Dispersant)J1899_202010-TEST-REC (Historical)10/28/2020
This SAE Standard establishes the requirements for lubricating oils containing ashless dispersant additives to be used in four-stroke cycle, reciprocating piston aircraft engines. This document covers the same lubricating oil requirements as the former military specification MIL-L-22851. Users should consult their airframe or engine manufacturers manuals for the latest listing of acceptable lubricants.
E-38 Aviation Piston Engine Fuels and Lubricants
Measurement of the Total Ash Content of Aviation Piston Engine Oils by a Calculation MethodJ1787_202009 (Current)09/29/2020
This SAE Recommended Practice describes an empirical method for determining the theoretical ash content of aviation piston engine lubricating oils by calculating the equivalent weight of metallic oxides formed at 775 °C based on the metallic elemental concentration. The calculation method of ash determination may be used as an alternate to ASTM D 482 for application to the standards for aviation piston engine lubricating oils.
E-38 Aviation Piston Engine Fuels and Lubricants
Measurement of the Total Ash Content of Aviation Piston Engine Oils by a Calculation MethodJ1787_202009-TEST-REC (Historical)09/29/2020
This SAE Recommended Practice describes an empirical method for determining the theoretical ash content of aviation piston engine lubricating oils by calculating the equivalent weight of metallic oxides formed at 775 °C based on the metallic elemental concentration. The calculation method of ash determination may be used as an alternate to ASTM D 482 for application to the standards for aviation piston engine lubricating oils.
E-38 Aviation Piston Engine Fuels and Lubricants
SMART Solar SailTBMG-3720507/01/2020
The SMART (Super Miniaturized Autonomous Reconfigurable Technology) Solar Sail is a deployable, fully autonomous solar sail for use in very fine station-keeping of a spacecraft. The solar sail would be highly deformable from an initially highly compressed configuration, yet also capable of enabling very fine maneuvering of the spacecraft by means of small sail-surface deformations.
Preignition Rating of Spark PlugsJ549_202006 (Current)06/15/2020
This SAE Recommended Practice describes the equipment and procedures used in obtaining preignition ratings of spark plugs.
Ignition Standards Committee
Elastomer: Methyl Phenyl Vinyl Silicone (PVMQ) Very Low Temperature/Aircraft Piston Engine Oil Resistant High Strength/Tear Resistant 45 to 55 Durometer Type ‘A’ Hardness For Products in Aircraft Piston Engine Oil/Low Temperature EnvironmentsAMS3345G (Current)05/18/2020
This specification covers a methyl phenyl vinyl silicone rubber material that can be used to manufacture product in the form of sheet, strip, tubing, molded shapes, and extrusions. For molded rings, compression seals, O-ring cord, and molded-in-place gaskets for aeronautical and aerospace applications, use the corresponding AMS7000 series specification.
AMS CE Elastomers Committee
Elastomer: Methyl Phenyl Vinyl Silicone (PVMQ) Very Low Temperature/Aircraft Piston Engine Oil Resistant High Strength/Tear Resistant 45 to 55 Durometer Type ‘A’ Hardness For Products in Aircraft Piston Engine Oil/Low Temperature EnvironmentsAMS3345G-TEST-REC (Historical)05/18/2020
This specification covers a methyl phenyl vinyl silicone rubber material that can be used to manufacture product in the form of sheet, strip, tubing, molded shapes, and extrusions. For molded rings, compression seals, O-ring cord, and molded-in-place gaskets for aeronautical and aerospace applications, use the corresponding AMS7000 series specification.
AMS CE Elastomers Committee
Supersonic Spike DiffuserTBMG-3682405/01/2020
The basic mode of operation for all passive supersonic diffusers is to enable a plume’s inherent power to drive the outer boundary of the exhaust jet to the diffuser wall so that the entire cross-section of the flow has a speed greater than that of sound. This allows mass removal from the area surrounding the nozzle via entrainment. The result is a low-pressure environment similar to the altitude at which the nozzle was designed to operate. Additionally, the nature of supersonic flow prevents pressure interference from the downstream environment.
Influence of Port Water Injection on the Combustion Characteristics and Exhaust Emissions in a Spark-Ignition Direct-Injection Engine2020-01-029404/14/2020
It is well known that engine downsizing is still the main energy-saving technology for spark-ignition direct-injection (SIDI) engine. However, with the continuous increase of the boosting ratio, the gasoline engine is often accompanied by the occurrence of knocking, which has the drawback to run the engine at retarded combustion phasing. Besides, in order to protect the turbine blades from being sintered by high exhaust temperature, the strategies of fuel enrichment are often taken to reduce the combustion temperature, which ultimately leads to a high level of particulate number emission. Therefore, to address the issues discussed above, the port water injection (PWI) techniques on a 1.2-L turbocharged, three-cylinder, SIDI engine were investigated. Measurements indicate that the optimization of spark timing has a significant impact on its performance. The two factors of the water substance itself and spark advance caused by the knock mitigation are trade-offs, which eventually affect
Fan, Yadong, Wu, Tianbao, Li, Xuesong, Xu, Min, Hung, David
Numerical Investigation of the Effects of Port Water Injection Timing on Performance and Emissions in a Gasoline Direct Injection Engine2020-01-028704/14/2020
Port water injection is considered as a promising strategy to further improve the combustion performance of internal combustion engines for its benefit in knock resistance by reducing the cylinder temperature. A thorough investigation of the port water injection technique is required to fully understand its effects on the engine combustion process. This study explores the potential of the port water injection technique in improving the performance of a turbo charged Gasoline Direct Injection engine. A 3D computational fluid dynamics model is applied to simulate the in-cylinder mixing and combustion for this engine both with and without water injection. Different water injection timings are investigated and it is found that the injection timing greatly effects the mass of water which enters the combustion chamber, both in liquid and vapor form. Comparison have been given between the original engine and the water injection one and the results show that the water injection can reduce the
Yin, Peng, Li, Xuesong, Hung, David, Fan, Yadong, Xu, Min
Experimental Analysis of a Multiple Radiator Cooling System with Computer Controlled Flow Rates2020-01-094404/14/2020
The automotive cooling system configuration has remained fixed for many decades with a large radiator plus fan, coolant pump, and bypass valve. To reduce cooling system power consumption, the introduction of multiple computer-controlled heat exchangers may offer some benefits. A paradigm shift from a single large radiator, sized for maximum load, to n-small radiators with individual flow control valves should allow fine tuning of the heat rejection needs to minimize power. In this project, a series of experimental scenarios featuring two identical parallel radiators have been studied for low thermal load engine cooling (e.g., idling) in ground transportation applications. For high thermal load scenarios using two radiators, the fans required between 1120 - 3600 W to maintain the system about the coolant reference temperature of 85oC. In contrast at reduced thermal loads, a single radiator configuration with half the heat transfer surface area required between 550 - 1000 W for the same
Syed, Zaker, Wagner, John
Temperature Measurement, Well Insert TypeARP175A (Current)04/14/2020
A-4 Aircraft Instruments Committee
Limiting Creep in Aerospace MaterialsTBMG-3661304/01/2020
The Larson-Miller parameter was first used in the 1950s as a model to predict the lifetime of a material vs. time and temperature. Without close attention to materials selection, many products are not fit for purpose due to mechanical stress and natural creep. That’s why creep resistant materials are so important in the aerospace industry.
The impacts of Diesel cycle engines on the operating costs of the Cessna 172 Skyhawk and JT-A aircraft.2019-36-032101/13/2020
Diesel engines have been used on the aeronautical market for a long time. Despite this fact, there are few studies showing the potential cost savings of using this type of technology. In this way, the goal of this paper is to find out whether or not it is advantageous to use an Otto or Diesel cycle engine on general aviation light aircraft. It is well known that both of them have pros and cons, however, the possibility of using Jet A-1 (kerosene) as fuel gives the Diesel engine a clear advantage in a market like Brazil, where the price of the regular piston fuel (AvGas) keeps rising to astonishing values. Throughout this paper, a detailed study of the fixed and variable costs of two similar aircraft, both Cessnas 172 equipped with Otto and Diesel cycle engines is conducted, comparing fuel consumption, performance levels, and other factors. Even though the latter engine has a higher fixed operating cost, the advantages found in this study makes the Diesel motor a step forward of its
Diniz, Samuel Cunha, Henrique de Assis Coelho, Eduardo, Rodrigues de Oliveira, Gabriel, de Cardoso Oliveira, Lucas, Morais, Samuel Renan Costa, Vasques, Victor Britto, Jorge Machado, Luiz Henrique
Using Engine Test Data to Model Engine PerformanceAIR5509A (Current)11/05/2019
This document defines the process steps involved in collecting and processing engine test data for use in understanding engine behavior. It describes the use of an aero-thermal cycle model for reduction and analysis of those data. The analysis process may include the calculation of modifiers to match the model to measured data and prediction of engine performance based on that analysis.
S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces
Aircraft Engine Icing Event Avoidance and MitigationTBMG-3473807/01/2019
Innovators at NASA’s Glenn Research Center have developed a new means of avoiding and mitigating icing events for aircraft flying above 14,000 feet, dramatically improving aviation safety and reducing operating costs.
SAE 17.6 Cubic Inch Spark Plug Rating EngineJ2203_201906 (Current)06/11/2019
This SAE Standard defines the standard engine to be used in determining spark plug preignition ratings. The engine is known as the SAE 17.6 Cubic Inch Spark Plug Rating Engine.
Ignition Standards Committee
High Power-Density, High Efficiency, Mechanically Assisted, Turbocharged Direct-Injection Jet-Ignition Engines for Unmanned Aerial Vehicles01-12-01-000205/02/2019
More than a decade ago, we proposed combined use of direct injection (DI) and jet ignition (JI) to produce high efficiency, high power-density, positive-ignition (PI), lean burn stratified, internal combustion engines (ICEs). Adopting this concept, the latest FIA (Fédération Internationale de l’Automobile) F1 engines, which are electrically assisted, turbocharged, directly injected, jet ignited, gasoline engines and work lean stratified in a highly boosted environment, have delivered peak power fuel conversion efficiencies well above 46%, with specific power densities more than 340 kW/liter. The concept, further evolved, is here presented for unmanned aerial vehicle (UAV) applications. Results of simulations for a new DI JI ICE with rotary valve, being super-turbocharged and having gasoline or methanol as working fuel, show the opportunity to achieve even larger power densities, up to 430 kW/liter, while delivering a near-constant torque and, consequently, a nearly linear power curve
Boretti, Alberto
Computational Optimization of Pressure Wave Reflection on the Piston Surface for Single Point Autoignition Gasoline Engine with Colliding Pulsed Supermulti-Jets Leading to Noiseless-High Compression and Nearly-Complete Air-Insulation2019-01-023504/02/2019
A new engine concept based on pulsed supermulti-jets colliding at a small area around the chamber center was proposed in our previous research. It was expected to provide noiseless high compression ratio and nearly-complete air-insulation on chamber walls, leading to high thermal efficiency. In the previous reports, three-dimensional computations for the unsteady compressible Navier-Stokes equation were conducted, which were qualitative because of using regular grid method. This time, we develop a new numerical code in order to quantitatively simulate the compression level caused by the jets colliding with pulse. It is achieved by applying a staggered grid method to improve conservatibity of physical quantities at very high compression in combustion phenomena. Computations at a simple condition were fairly agreed with a theoretical value. Computational results obtained for a complex geometry of an engine by the new code had less error than one with previous codes. In addition, the
Hosoi, Aya, Konagaya, Remi, Kawaguchi, Sota, Sogabe, Yasuhiro, Yamashita, Yuya, Naitoh, Ken
Supplemental Propulsion System Performance Station DesignationAIR6508 (Current)01/03/2019
This SAE Aerospace Information Report (AIR) supplements the AS755 performance station designation system for complex or unconventional propulsion cycles and their derivatives. The station numbering conventions presented herein are for use in all communications concerning propulsion system performance such as computer programs, data reduction, design activities, and published documents. They are intended to facilitate calculations by the program user without unduly restricting the method of calculation used by the program supplier. The contents of this document will follow AS755 and AS6502 where applicable. The list of symbols presented herein will be used for identification of input and output parameters. These symbols are not required to be used as internal parameter names within the engine subprogram.
S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces
PROPELLER SHAFT ENDS - FLANGED SMALL AIRCRAFT ENGINEARP502A (Current)11/28/2018
E-25 General Standards for Aerospace and Propulsion Systems
Measurement Data and Reference Values for Compounds Potentially Found in Aircraft Engine Bleed AirAIR7521 (Current)10/09/2018
This document summarizes published measurement data and reference values for marker chemical compounds listed in ARP4418 (see 2.1.1) potentially found in aircraft engine bleed air.
E-31B Bleed Air Committee
Modeling of Ducted-Fan and Motor in an Electric Aircraft and a Preliminary Integrated Design01-11-02-000710/04/2018
Electric ducted-fans with high power density are widely used in hybrid aircraft, electric aircraft, and VTOL vehicles. For the state-of-the-art electric ducted-fan, motor cooling restricts the power density increase. A motor design model based on the fan hub-to-tip ratio proposed in this article reveals that the thermal coupling effect between fan aerodynamic design and motor cooling design has great potential to increase the power density of the motor in an electric propulsion system. A smaller hub-to-tip ratio is preferred as long as the power balance and cooling balance are satisfied. Parametric study on a current 6 kW electric ducted-fan system shows that the highest motor power density could be increased by 246% based on the current technology. Finally, a preliminary design was obtained and experiments were conducted to prove the feasibility of the model.
Jin, Yuzhi, Qian, Yuping, Zhang, Yangjun, Zhuge, Weilin
Burner Rig Testing of A500® C/SiCTBMG-3302410/01/2018
There is growing interest in developing, testing, and deploying ceramic-matrix composites (CMCs) into commercial and military aerospace gas turbine engines due to their durability under extreme conditions and weight-savings potential. For military applications, the focus is on the afterburning section of the turbine engine, including the flameholder, augmentor liner, and both the convergent and divergent segments of the exhaust nozzle. These are demanding applications because of the high temperatures and rapid thermal cycles.
Impact of Engine Age and Engine Hardware on Low-Speed Pre-Ignition2018-01-166309/10/2018
Low-speed pre-ignition (LSPI) is a well-studied phenomenon in boosted, spark ignition engines. The impact of lubricant formulation has received a lot of attention in recent years, yet the impact of engine hardware and engine wear on LSPI is still not fully understood. This paper addresses some of these questions using results from multiple installations of the GM 2.0 L LHU engine platform. In the first part of the study, the effect of engine life on LSPI activity was observed, and it was found that engines were susceptible to variations in LSPI activity during the initial LSPI tests with the activity eventually reaching a “stabilized” level. It was further observed that the LSPI activity generally continued to decline at a steady rate as the engine aged. For engines used in LSPI testing, the life of the engine is often limited as LSPI activity decays with age. This reduction in LSPI activity may correlate to the engine liner wear and it is suggested that the amount of oil transport
Kalaskar, Vickey B., Swarts, Andre, Alger, Terrence
Selected Aerospace Diameter Pitch Combinations of Metric 60° Screw Threads for Nuts and BoltsAS1337A (Current)08/23/2018
This Aerospace Standard establishes the preferred diameter-pitch combinations of ISO metric 60° screw threads recommended for use in the aerospace industry for metric module bolts and nuts.
E-25 General Standards for Aerospace and Propulsion Systems
Horsepower Correction FormulaeARP2C (Current)08/09/2018
This document discusses formulae considered applicable to aircraft engines having integral supercharging without aftercooling, and using gasoline introduced at the entrance to the supercharger or directly into the cylinders. Such engines are normally designated as single and two speed engines. Correction formulae for engines having two stage or exhaust turbo supercharging will not be discussed. Corrections for engines having a high degree of integral supercharging will be discussed in general terms only and no specific formulae will be presented. The correction formulae and methods listed are empirical and subject to error due to conditions beyond the scope of known corrections. Usage has indicated, however, that the correction formulae listed will provide a satisfactory approximation of power output under standard conditions.
E-25 General Standards for Aerospace and Propulsion Systems
Super-Turbocharging the Gasoline Engine2018-28-000707/09/2018
In this paper, the concept of super-turbocharging is applied, in simulation, to a four-cylinder direct injection jet ignition gasoline engine. Turbocharging improves the power density of internal combustion engines, both the compression ignition and the spark ignition. However, a standalone turbocharger suffers from transient and steady state performance and efficiency degradation where the energy to turbine is either smaller or larger than what would be needed to optimize the engine operation in a specific point. Hence a concept is proposed to use a super-turbocharger, where the turbocharger shaft is connected to the crankshaft through a continuously variable transmission (CVT) and a gears pair. Energy is drawn from the crankshaft or delivered to the crankshaft to better work in every operating point. The concept was originally proposed for a diesel engine. Here it is applied to a gasoline engine. Results of simulations of engine performance are presented and discussed, prompting a
Boretti, Alberto
Definitions, Aircraft Reciprocating Engine PerformanceAS20D (Current)06/20/2018
This document lists definitions that are commonly used in describing aircraft reciprocating engine performance.
E-25 General Standards for Aerospace and Propulsion Systems
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